US3902819A - Method and apparatus for cooling a turbomachinery blade - Google Patents

Method and apparatus for cooling a turbomachinery blade Download PDF

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Publication number
US3902819A
US3902819A US367052A US36705273A US3902819A US 3902819 A US3902819 A US 3902819A US 367052 A US367052 A US 367052A US 36705273 A US36705273 A US 36705273A US 3902819 A US3902819 A US 3902819A
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United States
Prior art keywords
blade
fluid
passages
header
coolant
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Expired - Lifetime
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US367052A
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English (en)
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Jacob Holchendler
David Japikse
William F Laverty
James J Wesbecher
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RTX Corp
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United Aircraft Corp
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Priority to US367052A priority Critical patent/US3902819A/en
Priority to SE7407007A priority patent/SE390324B/xx
Priority to CA201,448A priority patent/CA1005346A/en
Priority to JP49063287A priority patent/JPS5048310A/ja
Priority to FR7419156A priority patent/FR2231846B1/fr
Priority to GB2479174A priority patent/GB1468595A/en
Priority to DE19742426924 priority patent/DE2426924A1/de
Application granted granted Critical
Publication of US3902819A publication Critical patent/US3902819A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/185—Liquid cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • thermosyphon systems have been used previously.
  • Ledinegg U.S. Pat. No. 2,667,326 a closed loop thermosyphon cooling system is used, however, the coolant is evaporated in a single pass through the turbine blade, and thence is returned to a remote heat sink in the turbomachinery disc for condensation prior to recirculation through the turbine blades.
  • geometric separation of the coolant inlet and outlet from the blades is made possible only by the presence of different phases at the inlet and the outlet.
  • thermosyphon blade cooling system which is open loop and utilizes water as its cooling fluid, however, the system is single pass and the cooling media is passed through the turbine blade but a single time and is then discharged overboard. In addition, no special effort is made to deliberately define and separate the inlet and exit coolant flow location.
  • Bruckmann U.S. Pat. No. 2,779,565 is similar to Eckert, albeit air is used as the cooling media but in single-pass fashion.
  • Schneider U.S. Pat. No. 3,623,825 utilizes liquid metal, without phase change. in aparticular portion of a heat exchanger within the blade in a sealed compartment and thereby presents sealing, maintainability, and weight problems.
  • a primary object of the present invention is to provide an improved method and hardware for cooling turbomachinery blading utilizing an open, mixed convection thermosyphon system within the blade.
  • the turbomachinery blade coolant is preferably steam at high pressure and at temperature above critical, into which coolant at low temperature, and high pressure is injected in order to create a concentrated heat sink and thereby establish a density differential so as to produce continuous thermosyphon multi-pass pumping of the coolant.
  • a selected amount of cooling fluid is discharged from the system at the same rate at which the low temperature coolant is added to the system to maintain system pressure and coolant mass at a selected level.
  • inlet and exit flow rates may differ.
  • the coolant flow within the blade is at a rate many times as great (frequently tenfold or more) as the rate of injection of low temperature coolant thereby minimizing the variation of coolant temperature in the different parts of the blade, giving a high heat transfer coefficient as required to cool the blade while avoiding the problems associated with change of phase (particularly boiling), and making the cooling system thermodynamically efficient.
  • the turbomachinery blade be fabricated so as to include a coolant loop therewithin comprising an outer header extending substantially along the blade tip, an inner header extending substantially along the blade root, and passages or conduits extending between the headers, and further preferably including a blade trailing edge header and a discharge passage or passages joined to the main coolant loop through an orifice so as to permit the extraction of fluid from the cooling loop in a selective fashion so as to maintain system pressure and fluid mass at desired levels and to regulate the mixing process at the inlet location.
  • a coolant loop therewithin comprising an outer header extending substantially along the blade tip, an inner header extending substantially along the blade root, and passages or conduits extending between the headers, and further preferably including a blade trailing edge header and a discharge passage or passages joined to the main coolant loop through an orifice so as to permit the extraction of fluid from the cooling loop in a selective fashion so as to maintain system pressure and fluid mass at desired levels and to regulate the mixing process at the inlet location.
  • the fluid extracted from the system is used for cooling purposes, and preferably to cool the blade trailing edge.
  • FIG. 1 is a showing of turbomachinery utilizing this invention.
  • FIG. 2 is a cross-sectional drawing through a turbo machinery blade utilizing the present invention but the number of coolant passages have been reduced to better permit description.
  • FIG. 3 is a view taken along line 3-3 of FIG. 2 and shows a representative number of coolant passages.
  • turbomachinery unit 1 which may be a gas or steam turbine or compressor, and which comprises at least one rotor 2 mounted for rotation about axis 3 and including a disc 4 supporting a plurality of blades 10 about the periphery thereof.
  • Rotor 2 is mounted within housing 5, from which vaned stator 6 projects to control the angle of entry of the gas flowing through turbomachinery 1 as it approaches blades 10.
  • turbomachinery blade 10 which includes blade tip 12, blade root 14, leading edge 16, trailing edge 18, and airfoil portion 20 extending between root l4 and tip 12.
  • Blade 10 is adapted to be supported from a rotor disc 2 of a turbomachinery compressor or turbine, for example, to be rotated therewith during turbine engine operation and to have hot gases passed thereover so that the blade is operating both in a high temperature environment and a strong centrifugal force environment.
  • a turbomachinery blade and its associated turbine and/or compressor parts reference may be had to US. Pat. Nos. 2,711,631 and 2,747,367.
  • Blade 10 is fabricated so that coolant loop 22 is positioned therewithin and includes outboard header 24 extending along the blade tip 12, inboard header 26 extending along the blade root l4, and outflow passage 28 and inflow heat exchanger passages extending between these headers and with passages 30 located adjacent to the blade convex and concave surfaces 29 and 31.
  • the cooling system also includes blade trailing edge header 32 which communicates with inboard header 26 through choked orifice 34, and which communicates with the gas flow passage external of blade 10 through a plurality of apertures 36 extending along and through the blade trailing edge 18. Coolant pressure and temperature levels in loop 22 are controlled by the sizing of orifice 34. Orifice 34 is preferably adjacent to inner header 26 but could be adjacent to outer header 28.
  • Blade 10 may be fabricated in any convenient fashion, for example, blade outer portion 38, which includes blade tip 12 and airfoil section 20 may serve as a blade wall member into which blade internal portion may extend in projecting from root 14 in blade-Scabbard fashion, thereby defining those passages enumerated above the blade outer portion 38 and blade inner portion would be sealably connected by welding or the like.
  • the preferred cooling fluid in coolant passage 22 is water in the form of steam operating at supercritical temperature and pressure to form an open, mixed convection-thermosyphon cooling system.
  • This supercritical steam passes outwardly from inboard header 26 through passage 28 to outboard header 24 and therefrom inwardly through passages 30 to inboard header 26 and recirculation again outwardly through passage 28 in multi-pass fashion.
  • passage 28 is located in a central portion of the blade while the heat exchanger passages 30 are located near the blade outer surfaces 29 and 31.
  • the motive force to create this circulation is derived from the heat sink positioned near the blade root 14 in passage 28, specifically at the end of tube member 42 through which water, at supercritical pressure but at a temperature lower than the supercritical steam is injected into the inner end of passage 28.
  • this low temperature coolant from conduit 42 serves to lower the temperature of the coolant in conduit 28 below the temperature of the coolant in conduits 30 to establish both a temperature and density differential therebetween, thereby establishing a continuing flow of the coolant in cooling fluid system 22 outwardly through passage 28 into outer header 24, and then inwardly through passages 30 to inner header 26, and continued recirculation through this route as desired to effect blade'cooling.
  • a selected amount of coolant is discharged through orifice 34 into blade trailing edge header 32, from which it is discharged to gas flow path 35 through blade trailing edge apertures 36 for the purpose of cooling the blade trailing edge.
  • Orifice 34 is sized so that the rate of coolant so discharged is at the same flow rate at which the low temperature coolant is entering the system through conduit 42.
  • Low temperature coolant for conduit 42 may be stored and/or supplied in any convenient fashion, such as within or from the rotor disc 2. In this fashion, an open, mixed convention thermosyphon cooling system is established.
  • This system therefore effects coolant (supercritical steam) recirculation by low temperature coolant (water) injection and this provides a uniqueness to our system over other known thermosyphon systems in that our system establishes a flow rate in coolant which is on the order of 10 times as great as the flow rate of the injected low temperature coolant and this has the advantages of minimizing the variation of coolant temperature in the different parts of blade 10, giving the high heat transfer coefficients required to cool the blade while avoiding the problems associated with change of phase of the coolant, particularly boiling, and making the cooling system thermodynamically efficient.
  • the present coolant system is said to be open because the coolant fluid is being discharged from the system through trailing edge ports 36, is said to be mixed convection since the system operates by both free and forced convection, and is said to be a thermosyphon because the continuous pumping and recirculation of the coolant is brought about by the functioning of the heat sink to establish density differentials within the cooling system 22.
  • the heat added to blade 10 during operation for given external (gas-side) conditions is proportional to the temperature level and flow rate of the recirculating coolant which is proportional in turn, to the flow rate of injected coolant. It will therefore be seen that this system functions as a convective (or thermal) amplifier.
  • the three main elements of this blade cooling system are: (l) a coolant loop 22 within the blade 10, (2) a low temperature coolant injection system (conduit 42) which is used to produce the pumping force to circulate the coolant in the loop 22, and (3) a discharge orifice system 32-36 to exhaust spent coolant to the turbomachinery gas path and maintain the required coolant pressure and mass level in the blade.
  • the cooling of the blade is primarily accomplished by the transfer of heat to the supercritical water flowing radially inwardly through the heat exchanger passages 30
  • supercritical steam in inner header 26 is at 950F
  • water at F is introduced thereinto through conduit 42 in the lower part of outflow passage 28 so as to produce a mixed temperature therein of 900F.
  • This 900 water will flow into tip header 24 and then flow back to the inner header 26 through exchanger tubes or passages 30 wherein heat transfer from the passage walls causes the supercritical steam to be elevated to the 950 temperature by the time it reaches inner header 26.
  • the mean or average temperature of the supercritical steam in the heat exchanger passages 30 is 925 and that the temperature of the supercritical steam in passage 28 is 900, giving a 25F temperature differential.
  • This temperature differential produces a density differential so that the more dense supercritical steam at 900 will be acted upon to a greater degree by the centrifugal force generated by the rotating rotor 2 than the less dense supercritical steam in heat exchanger conduits 30, thereby establishing the pumping force action of the thermosyphon principle which will cause the fluid to so continue to circulate through coolant loop 22, so long as this temperature differential, and hence the density differential, is maintained.
  • the cool water at 100F is continuously injected into the inner end of passage 28 and supercritical steam is discharged from the system at an equal rate to maintain the pressure and mass of the coolant in loop 22 at desired levels.
  • supercritical steam is discharged from the system at an equal rate to maintain the pressure and mass of the coolant in loop 22 at desired levels.
  • a turbomachinery blade adapted to be mounted for rotation on a disc and to have hot gas pass thereover so as to thereby be subjected to both centrifugal force and high temperature including:
  • heat sink establishing means acting upon the cooling fluid in one portion of said loop to establish a temperature and hence a density differential between the cooling fluid in different parts of said coolant loop to thereby establish a continuous cir culatory flow and recirculation of cooling fluid within the coolant loop utilizing the thermal syphon principle
  • said heat sink establishing means comprises a means for injecting a coolant at lesser temperature than the cooling fluid into said coolant loop at a selected location, and means to discharge cooling fluid from the coolant loop at the same rate that coolant is being injected into the coolant loop to thereby maintain selected pressure level and coolant mass in the coolant loop.
  • a blade according to claim 3 which blade has discharged slots in the blade trailing edge and wherein the fluid is discharged through said trailing edge slots.
  • a blade according to claim 1 wherein said blade comprises an outer cover defining the blade tip and airfoil section walls and an inner member inserted thereinto in blade-in-scabbard fashion and sealably connected thereto. with both the blade outer cover portion and the blade inner portion being selectively shapedto define said coolant loop.
  • thermosyphon principle 8. The method of cooling a turbomachinery blade utilizing the thermosyphon principle including the steps of: i
  • a turbomachinery blade adopted to be mounted for rotation on a disc and to have hot gas passed thereover so as to thereby be subjected both to centrifugal force and high temperature including:
  • a blade airfoil section shaped to define the blade tip, the blade leading edge and trailing edge and attached to the blade root to extend radially outwardly therefrom when the blade is mounted on the disc and shaped to define therewithin a selectively shaped passage system including a series of substantially radially extending passage joining an outboard header and an inboard header,
  • thermosyphon principle including the steps 1. providing a plurality of substantially radially extending passages in the blade interior joining a header extending along the blade tip and a header extending along the blade root,
  • said last step includes cooling the temperature of the fluid in at least one of the passages by direct heat sink injection to increase its density so that, in accordance with the thermosyphon principle, the more dense fluid will flow radially outwardly to the tip header and the less dense fluid will flow radially inwardly to the root header establish blade coolant circulation.
  • thermosyphon principle including the steps of:
  • cooling fluid is supercritical and wherein water at a temperature less than the supercritical is introduced to one of the passages to establish a heat sink to produce the desired density differential, and wherein supercritical steam is bled from the system at the same rate that cooling water is added to the system to maintain the coolant mass pressure, and the density differential substantially constant in the system.
  • thermosyphon principle including the steps of:
  • thermosyphon principle including the steps of:
  • a turbomachinery blade adapted to be mounted for rotation on a disc and to have hot gas passed thereover so as to thereby be subjected both to centrifugal force and high temperature including:
  • a blade airfoil section shaped to define the blade tip, the blade leading edge and trailing edge and attached to the blade root to extend radially outwardly therefrom when the blade is mounted on the disc and shaped to define therewithin a passage system including a series of substantially radially extending passages joining an outboard header and an inboard header,
  • a turbomachinery blade adapted to be mounted for rotation on a disc and to have hot gas passed thereover so as to thereby be subjected both to centrifugal force and high temperature including:
  • a blade airfoil section shaped to define the blade tip, the blade leading edge and trailing edge and attached to the blade root to extend radially outwardly therefrom when the blade is mounted on the disc and shaped to define therewithin a passage system including a series of substantially radially extending passages joining an outboard header and an inboard header,
  • said blade has at least one aperture in the blade trailing edge and wherein the extracted fluid is discharged through apertures in the blade trailing edge to cool the blade trailing edge.
  • a turbomachinery blade adapted to be mounted for rotation on a disc and to have hot gas passed thereover so as to thereby be subjected both to centrifugal force and high temperature including:
  • a blade airfoil section shaped to define the blade tip, the blade leading edge and trailing edge and attached to the blade root to extend radially outwardly therefrom when the blade is mounted on the disc and shaped to define therewithin a passage system including a series of substantially radially extending passages joining an outboard header and an inboard header,
  • said density differential establishing means including:
  • said blade has at least one aperture in the blade trailing edge and wherein the extracted fluid is discharged through apertures in the blade trailing edge to cool the blade trailing edge, and, still further, wherein said fluid extraction means includes an orifice joining one of said headers to a blade trailing edge header which is connected to the hot gas stream through said blade trailingedge apertures.
  • a turbomachinery blade adapted to be mounted for rotation on a disc and to have hot gas passed thereover so as to thereby be subjected both to centrifugal force and high temperature including:
  • a blade airfoil section shaped to define the blade tip, the blade leading edge and trailing edge and attached to the blade root to extend radially outwardly therefrom when the blade is mounted on the disc and shaped to define therewithin a passage system including a series of substantially radially extending passages joining an outboard header and and inboard header,
  • said density differential establishing means including:
  • said blade has at least one aperture in the blade trailing edge and wherein the extracted fluid is discharged through apertures in the blade trailing edge to cool the blade trailing edge, and, still further, wherein said fluid extraction means includes an orifice joining one of said headers to a blade trailing edge header which is connected to the hot gas stream through said blade trailing edge apertures, and wherein said one header is the inboard header.
  • a turbomachinery blade adpated to be mounted for rotation on a disc and to have hot gas passed thereover so as to thereby be subjected both to centrifugal force and high temperature including:
  • a blade airfoil section shaped to define the blade tip, the blade leading edge and trailing edge and attached to the blade root to extend radially outwardly therefrom when the blade is mounted on the disc and shaped to define therewithin a passage system including a series of substantially radially extending passages joining an outboard header and an inboard header,
  • trailing edge header which is connected to the hot gas stream through said blade trailing edge apertures, and wherein said orifice is caused to operate in chocked condition.
  • a blade airfoil section shaped to define the blade tip, the blade leading edge and trailing edge and attached to the blade root to extend radially out- 5.
  • means 9 a coolmg l mto one of smd 5.
  • thermosyphim least one of said radial passages and said inboard clrculatlon and reclrculatlon of fluld m the gravity 2 header In multi pass recirculafion fashion and 2 field and I I I wherein said density differential establishing means inmeans to extract fluld from sald passage system at the same rate that the cooling fluid is being introcludmg: quizd to said passage system, and, further, wherein means 9 mjecl a coolmg fluld one of Sald passaid blade has at least one aperture in the blade Sages Coolmg fluld being f f" trailing edge and wherein the extracted fluid is ture than the temperature of the clrculatlng fluld in charged through apertures in the blade trailing the other passages to thereby stabl sh a temper aedge to cool the blade trailing edge andI still ture dlfferentlal and hence a denslty dlfferentlal ther, wherein said fluid
  • said system circulatory fluid is steam above critical pressure and temperature and wherein said lower temperature cooling fluid is water above critical pressure and at low temperature.
  • a turbomachinery blade adapted to be mounted for rotation on a disc and to have hot gas passed thereover so as to thereby be subjected both to centrifugal force and high temperature including:

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US367052A 1973-06-04 1973-06-04 Method and apparatus for cooling a turbomachinery blade Expired - Lifetime US3902819A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US367052A US3902819A (en) 1973-06-04 1973-06-04 Method and apparatus for cooling a turbomachinery blade
SE7407007A SE390324B (sv) 1973-06-04 1974-05-28 Blad for turbomaskin med kylmedelsslinga
CA201,448A CA1005346A (en) 1973-06-04 1974-06-03 Method and apparatus for cooling a turbomachinery blade
JP49063287A JPS5048310A (enExample) 1973-06-04 1974-06-04
FR7419156A FR2231846B1 (enExample) 1973-06-04 1974-06-04
GB2479174A GB1468595A (en) 1973-06-04 1974-06-04 Method and apparatus for cooling a turbomachinery blade
DE19742426924 DE2426924A1 (de) 1973-06-04 1974-06-04 Verfahren und vorrichtung zum kuehlen einer turbomaschinenschaufel

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US367052A US3902819A (en) 1973-06-04 1973-06-04 Method and apparatus for cooling a turbomachinery blade

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US3902819A true US3902819A (en) 1975-09-02

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US (1) US3902819A (enExample)
JP (1) JPS5048310A (enExample)
CA (1) CA1005346A (enExample)
DE (1) DE2426924A1 (enExample)
FR (1) FR2231846B1 (enExample)
GB (1) GB1468595A (enExample)
SE (1) SE390324B (enExample)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3989412A (en) * 1974-07-17 1976-11-02 Brown Boveri-Sulzer Turbomachinery, Ltd. Cooled rotor blade for a gas turbine
US4118145A (en) * 1977-03-02 1978-10-03 Westinghouse Electric Corp. Water-cooled turbine blade
US4134709A (en) * 1976-08-23 1979-01-16 General Electric Company Thermosyphon liquid cooled turbine bucket
US4179240A (en) * 1977-08-29 1979-12-18 Westinghouse Electric Corp. Cooled turbine blade
EP0015500A1 (en) * 1979-02-28 1980-09-17 Kabushiki Kaisha Toshiba Liquid-cooled gas turbine blades and method of cooling the blades
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
US4350473A (en) * 1980-02-22 1982-09-21 General Electric Company Liquid cooled counter flow turbine bucket
US5098257A (en) * 1990-09-10 1992-03-24 Westinghouse Electric Corp. Apparatus and method for minimizing differential thermal expansion of gas turbine vane structures
US5240069A (en) * 1992-07-06 1993-08-31 The United States Of America As Represented By The Secretary Of The Air Force Integral cooling system for a jet engine integral starter/generator and the like
US5993155A (en) * 1997-03-29 1999-11-30 Asea Brown Boveri Ag Cooled gas-turbine blade
EP1013879A1 (de) * 1998-12-24 2000-06-28 Asea Brown Boveri AG Flüssigkeitsgekühlte Turbomaschinenwelle
US6988367B2 (en) 2004-04-20 2006-01-24 Williams International Co. L.L.C. Gas turbine engine cooling system and method
US20080199303A1 (en) * 2005-04-25 2008-08-21 Williams International Co., L.L.C. Gas Turbine Engine Cooling System and Method
US20110041509A1 (en) * 2008-04-09 2011-02-24 Thompson Jr Robert S Gas turbine engine cooling system and method
US9464527B2 (en) 2008-04-09 2016-10-11 Williams International Co., Llc Fuel-cooled bladed rotor of a gas turbine engine
EP3081782A4 (en) * 2013-12-12 2017-08-30 Industry-Academic Cooperation Foundation Yonsei University Supercritical fluid cooling gas turbine apparatus
US11913387B2 (en) 2022-03-24 2024-02-27 General Electric Company Method and apparatus for cooling turbine blades

Families Citing this family (2)

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Publication number Priority date Publication date Assignee Title
JPS57308A (en) * 1980-06-04 1982-01-05 Hitachi Ltd Moving vane for turbine
JP2013199925A (ja) * 2012-02-21 2013-10-03 Mitsubishi Heavy Ind Ltd ガスタービン設備

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US2750147A (en) * 1947-10-28 1956-06-12 Power Jets Res & Dev Ltd Blading for turbines and like machines
US2763427A (en) * 1949-10-13 1956-09-18 Armstrong Siddeley Motors Ltd Axial-flow machines
US2744723A (en) * 1949-12-06 1956-05-08 Thompson Prod Inc Controlled temperature fluid flow directing member
US2839268A (en) * 1950-01-18 1958-06-17 Allis Chalmers Mfg Co Gas turbine
US2737366A (en) * 1950-05-02 1956-03-06 Simmering Graz Pauker Ag Gas turbine
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US2883151A (en) * 1954-01-26 1959-04-21 Curtiss Wright Corp Turbine cooling system
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US3045965A (en) * 1959-04-27 1962-07-24 Rolls Royce Turbine blades, vanes and the like
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Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3989412A (en) * 1974-07-17 1976-11-02 Brown Boveri-Sulzer Turbomachinery, Ltd. Cooled rotor blade for a gas turbine
US4134709A (en) * 1976-08-23 1979-01-16 General Electric Company Thermosyphon liquid cooled turbine bucket
US4118145A (en) * 1977-03-02 1978-10-03 Westinghouse Electric Corp. Water-cooled turbine blade
US4179240A (en) * 1977-08-29 1979-12-18 Westinghouse Electric Corp. Cooled turbine blade
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
EP0015500A1 (en) * 1979-02-28 1980-09-17 Kabushiki Kaisha Toshiba Liquid-cooled gas turbine blades and method of cooling the blades
US4330235A (en) * 1979-02-28 1982-05-18 Tokyo Shibaura Denki Kabushiki Kaisha Cooling apparatus for gas turbine blades
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US5993155A (en) * 1997-03-29 1999-11-30 Asea Brown Boveri Ag Cooled gas-turbine blade
EP1013879A1 (de) * 1998-12-24 2000-06-28 Asea Brown Boveri AG Flüssigkeitsgekühlte Turbomaschinenwelle
US6988367B2 (en) 2004-04-20 2006-01-24 Williams International Co. L.L.C. Gas turbine engine cooling system and method
US20080199303A1 (en) * 2005-04-25 2008-08-21 Williams International Co., L.L.C. Gas Turbine Engine Cooling System and Method
US8057163B2 (en) 2005-04-25 2011-11-15 Williams International Co., L.L.C. Gas turbine engine cooling system and method
US20110041509A1 (en) * 2008-04-09 2011-02-24 Thompson Jr Robert S Gas turbine engine cooling system and method
US8820092B2 (en) 2008-04-09 2014-09-02 Williams International Co., L.L.C. Gas turbine engine cooling system and method
US9464527B2 (en) 2008-04-09 2016-10-11 Williams International Co., Llc Fuel-cooled bladed rotor of a gas turbine engine
EP3081782A4 (en) * 2013-12-12 2017-08-30 Industry-Academic Cooperation Foundation Yonsei University Supercritical fluid cooling gas turbine apparatus
US11913387B2 (en) 2022-03-24 2024-02-27 General Electric Company Method and apparatus for cooling turbine blades

Also Published As

Publication number Publication date
FR2231846B1 (enExample) 1978-07-07
CA1005346A (en) 1977-02-15
JPS5048310A (enExample) 1975-04-30
FR2231846A1 (enExample) 1974-12-27
SE390324B (sv) 1976-12-13
GB1468595A (en) 1977-03-30
SE7407007L (enExample) 1974-12-05
DE2426924A1 (de) 1975-01-02

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